N5040Q
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
CPS/LIT - WHILE ON FINAL, THE FLAP SYSTEM FAILED. IT WAS DETERMINED THE UPPER FLAP EXTEND CABLE ON THE RIGHT SIDE HAD BROKEN APPROXIMATELY A FOOT OUTBOARD OF THE ACTUATOR CHAIN ATTACH POINT. THE CABLE COULD HAVE BEEN INCORRECTLY ROUTED/RIGGED AND/OR THE CABLE TENSION COULD HAVE BEEN INCORRECTLY SET. THE CABLE WAS REPLACED ABOUT 10 HOURS PRIOR TO FAILURE. (X)
DURING THE COURSE OF NORMAL FLIGHT, THE PILOT NOTICED RIGHT ENGINE RUNNING ROUGH WITH A DROP IN ITS MANIFOLD PRESSURE. THE AIRCRAFT LANDED WITHOUT EVENT. MAINTENANCE WAS ABLE TO DETERMINE THAT THE NR 2 CYLINDER HEAD HAD SEPARATED FROM THE BARREL OF THE CYLINDER. THE DAMAGE WAS CONFINED TO THE CYLINDER, THE UPPER DECK LINES, INJECTOR LINES, INTAKE AND EXHAUST PIPES WERE ALL UNDAMAGED.
DURING THE COURSE OF COMPLETING A 100-HOUR INSPECTION, A CRACK WAS DISCOVERED IN THE FORWARD PORTION OF RIB, CESSNA P/N 0822175-74. THE RIB HAD BEEN MODIFIED IAW CESSNA SK 414-8E APPROXIMATELY 4,303 HOURS AGO, WHICH, BY LOCATION, IS NOT ASSOCIATED WITH THE CRACK SHOWN IN THE DRAWING.
DURING THE COURSE OF COMPLETING A 100-HOUR INSPECTION, MULTIPLE CRACKS WERE FOUND IN THE PRIMARY COMPONENTS THAT MAKE UP CESSNA SERVICE KIT SK404-83. CRACKS WERE FOUND ON BOTH LEFT AND RIGHT RIBS, FILLERS, DOUBLERS, AND ANGLES.
DURING THE COURSE OF COMPLETING A 100-HOUR INSPECTION, MULTIPLE CRACKS WERE FOUND IN THE PRIMARY COMPONENTS THAT MAKE UP CESSNA SERVICE KIT SK414-83. CRACKS WERE FOUND ON BOTH LEFT AND RIGHT RIBS, FILLERS, DOUBLERS, AND ANGLES.
DURING THE COURSE OF COMPLETING A 100-HOUR INSPECTION, A CRACK WAS DISCOVERED IN THE FORWARD PORTION OF RIB, CESSNA P/N 0822175-79. THE RIB HAD BEEN MODIFIED IAW CESSNA SK 414-8E APPROXIMATELY 4,303 HOURS AGO, WHICH, BY LOCATION, IS NOT ASSOCIATED WITH THE CRACK SHOWN IN THE DRAWING.
DURING 100-HOUR INSPECTION, MECHANIC NOTICED RIGHT ENGINE, NR 6 CYLINDER, PER MOST AFT AND THE LOWER TWO MOST AFT STUDS HAD BROKEN OFF FLUSH WITH THE CYLINDER BASE/SKIRT. THE CASE WAS INSPECTED FOR CRACKS, AND A CRACK APPROXIMATELY A .50 INCH LONG WAS OBSERVED COMING FROM THE LOWER STUD HOLE (JUST FORWARD OF THE MOST AFT LOWER STUD) WAS CRACKED IN THE DIRECTION OF THE CENTER OF THE ENGINE CASE. SUBMITTER STATED TO HAVING HAD THIS PROBLEM IN THE PAST AND HAD STARTED REPLACING THE CYLINDER BASE STUDS AT ENGINE OVERHAUL. UNFORTUNATELY, THESE STUDS WERE REPLACED AND HAVE APPROXIMATELY 300 HOURS TISN.
DURING THE COURSE OF A 100-HOUR INSPECTION, THE MECHANIC NOTICED A SIZEABLE AMOUNT OF OIL ON THE TOP LEFT PORTION OF THE ENGINE CASE. A CLOSER INSPECTION REVEALED A CRACK APPROXIMATELY 1.6250 INCH LONG EMITTING FROM THE 9TH BACKBONE BOLT (COUNTING FROM FRONT TO BACK). THE CRACK/CASE WAS INSPECTED IAW TCM SBM90-17 AND WAS DETERMINED TO BE UNAIRWORTHY DUE TO THE AMOUNT OF OIL LEAKING FROM SAID CRACK/CASE. THE CASE IN QUESTION HAS NOT BEEN REPAIRED/WELDED IN THE AREA AROUND THE CRACK. (THE CASE IS THE 'HEAVY' - 7TH STUD VERSION).
DURING A 100-HOUR INSPECTION, MECHANIC FOUND THE RIGHT TURBO MOUNTING BRACKET BROKEN. CESSNA BRACKET 0851139-3 HAD ITS OUTBOARD LOWER ATTACH LEG BROKEN OFF. UNABLE TO DETERMINE THE CAUSE OF THIS PROBLEM.
DURING NORMAL FLIGHT, PILOT NOTICED LEFT ENGINE RUNNING ROUGH AND RETURNED TO POINT OF DEPARTURE. DETERMINED THE NR 1 CYLINDER ON THE LEFT ENGINE HAD SEPARATED THE HEAD FROM THE BARREL. SUBMITTER SUGGESTED FROM PAST EXPERIENCE, THIS IS TYPICAL OF A TCM TSIO520 CYLINDER AND STATES THE ONLY COURSE OF ACTION THAT CAN BE TAKEN IS THOROUGH 50/100 HOUR INSPECTIONS.
UPON COMPLETING A NORMAL TRIP, THE PILOT ON HIS POST FLIGHT INSPECTION NOTICED THE RT INBOARD LANDING GEAR DOOR WAS OPEN. AFTER A CLOSER INSPECTION, DETERMINED THE BELLCRANK ASSEMBLY THAT ACTUATES THE INBOARD GEAR DOOR WAS BROKEN. IT WAS BROKEN IN SUCH A WAY THAT THE ONLY SYSTEM AFFECTED WAS THE GEAR DOOR. THE PART WAS SHOWING SIGNS OF BEING CRACKED FOR SOME TIME, THE PART APPEARS TO BE CONSTRUCTED OF 'CAST' STEEL, AND THERE WAS A DARKER PORTION APPROXIMATELY ONE-THIRD THE LENGTH OF THE BREAK INDICATING IT WAS AN OLD CRACK. THE PART RESTS BEHIND A BRACKET WHICH MAKES IT DIFFICULT TO INSPECT.
DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING. ALSO, TWO RIVETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TIP TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING. THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SECTION (CESSNA PN 0822040-18). SUSPECT CAUSES: TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING. ALSO, TWO RIVETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TIP TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING. THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SECTION (CESSNA PN 0822040-18). SUSPECT CAUSES: TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.
DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING. ALSO, TWO RIVETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TIP TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING. THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SECTION (CESSNA PN 0822040-18). SUSPECT CAUSES: TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STRUCK A SOLID OBJECT. AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUTING FACTOR.